Thermal management control device and method of fuel cell unmanned aerial vehicle and fuel cell unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and discloses a thermal management control device and method of a fuel cell unmanned aerial vehicle and the fuel cell unmanned aerial vehicle. The thermal management control device of the fuel cell unmanned aerial vehicle comprises a temperature sensor, an air flow channel control mechanism and a control unit, the temperature sensor is arranged in a fuselage of the fuel cell unmanned aerial vehicle to collect the environment temperature of a fuel cell, and a second air hole is formed in the fuselage to form a second air flow channel; the air flow channel control mechanism can selectively open or close the second air flow channel to increase or reduce heat dissipation of the fuel cell, and the control unit is in communication connection with the temperature sensor and the air flow channel control mechanism and controls the air flow channel control mechanism to open or close the second air flow channel according to the environment temperature. Automatic control over the environment temperature of the fuel cell is achieved, the problems that the air inflow of the fuel cell in the machine body is insufficient and the heat dissipation effect is poor are solved, and the working stability and environment adaptability of the fuel cell are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a thermal management control device and method for a fuel cell unmanned aerial vehicle and a fuel cell unmanned aerial vehicle. Background Art

[0002] The power sources of drones in the prior art include electricity and oil. With the development of clean energy, the application scope of various batteries has increased, and the batteries used in drones have gradually shifted from lithium batteries to fuel cells. The fuselage size of drones using lithium batteries is relatively small, and the fuel cell system cannot be completely placed inside the fuselage. Fuel cells generally use air cooling or air cooling systems. When the fuel cell is working, a large amount of air needs to be provided to ensure the oxygen supply in the electrochemical reaction, and air circulation is required to ensure the heat dissipation of the fuel cell system. In order to improve the protection level of existing lithium-powered drones, it is difficult to simultaneously meet the air intake and heat dissipation requirements of the fuel cell in the fuselage. The operation of the fuel cell needs to be kept within an appropriate temperature range, and the operation of the battery stack is an exothermic process, so the fuel cell needs to be thermally managed. Summary of the invention

[0003] The purpose of the present invention is to provide a thermal management control device, method and fuel cell drone for a fuel cell drone, so as to adapt to the development of fuel cell drones and solve at least one of the problems of existing drones, such as insufficient space, insufficient airway reservation, lack of thermal management system, etc.

[0004] To achieve this object, the present invention adopts the following technical solutions:

[0005] The thermal management control device of the fuel cell UAV includes:

[0006] A temperature sensor is disposed in the fuselage of the fuel cell drone to collect the ambient temperature of the fuel cell;

[0007] An air flow channel control mechanism, wherein a second air hole is provided on the fuselage to form a second air flow channel, and the air flow channel control mechanism can selectively open or close the second air flow channel to increase or reduce the heat dissipation of the fuel cell;

[0008] A control unit is communicatively connected to the temperature sensor and the air flow channel control mechanism, and the control unit controls the air flow channel control mechanism to open or close the second air flow channel according to the ambient temperature.

[0009] In some embodiments, the air flow channel control mechanism includes a diverter plate and a driving mechanism disposed at the second air hole, the driving mechanism is communicatively connected to the control unit, the output end of the driving mechanism is connected to the diverter plate, and the driving mechanism is used to drive the diverter plate to open or close the second air flow channel.

[0010] In some embodiments, the driving mechanism is fixedly mounted on the fuselage, and the driving mechanism drives the diverter plate to rotate toward the inside of the fuselage to open the second air flow channel, and the driving mechanism drives the diverter plate to rotate from the inside of the fuselage toward the second air hole to close the second air flow channel.

[0011] In some embodiments, two second air holes are provided, and the two second air holes are respectively arranged opposite to two fuel cells.

[0012] In some embodiments, a plurality of first air holes are spaced and dispersedly arranged on the bottom plate of the fuselage of the fuel cell drone to form a first air flow channel, and the fuel cell arranged in the fuselage is connected to the outside air through the first air flow channel to obtain oxygen and dissipate heat.

[0013] In some embodiments, the second air holes are disposed on both sides of the plurality of first air holes, and the diverter plate is rotatably disposed on a side of the second air holes close to the first air holes.

[0014] In some embodiments, the thermal management control device of the fuel cell drone also includes a cooling fan, which is arranged inside the fuselage, with an air inlet of the cooling fan facing the fuel cell and an air outlet of the cooling fan facing the outside of the fuselage.

[0015] The present invention also provides a thermal management control method for a fuel cell drone, which uses the thermal management control device for a fuel cell drone provided in any of the above embodiments. The thermal management control method for a fuel cell drone comprises the following steps:

[0016] Collecting the ambient temperature T of the fuel cell and sending it to the control unit;

[0017] According to the ambient temperature T, the control unit selectively opens or closes the second air flow channel through an air flow channel control mechanism.

[0018] In some embodiments, when the ambient temperature is greater than a first set temperature T1, the control unit controls the second air flow channel to be in an open state through the air flow channel control mechanism to increase the heat exchange between the fuel cell and the outside air; when the ambient temperature T is less than a second set temperature T2, the control unit controls the second air flow channel to be in a closed state through the air flow channel control mechanism to reduce the heat exchange between the fuel cell and the outside air; the first set temperature T1 is greater than the second set temperature T2.

[0019] In some embodiments, when the ambient temperature T is greater than the first set temperature T1, the control unit detects the state of the second air flow channel, and if the second air flow channel is in a closed state, the second air flow channel is opened through the air flow channel control mechanism, otherwise the second air flow channel is kept in an open state;

[0020] When the ambient temperature T is lower than the second set temperature T2, the control unit detects the state of the second air flow channel. If the second air flow channel is in a closed state, the closed state of the second air flow channel is maintained; otherwise, the second air flow channel is closed by the air flow channel control mechanism.

[0021] The present invention also provides a fuel cell drone, comprising the thermal management control device of the fuel cell drone provided in any of the above embodiments.

[0022] Beneficial effects of the present invention:

[0023] The thermal management control device of the fuel cell drone provided by the present invention arranges a second air hole on the fuselage to form a second air flow channel and arranges a temperature sensor in the fuselage to collect the ambient temperature and send it to the control unit, so that the control unit can control the air flow channel control mechanism to selectively open and close the second air flow channel according to the ambient temperature to increase or reduce the heat dissipation of the fuel cell, thereby realizing automatic control of the ambient temperature of the fuel cell, solving the problem of poor heat dissipation effect of the fuel cell in the fuselage, and improving the working stability and environmental adaptability of the fuel cell.

[0024] The thermal management control method for a fuel cell drone provided by the present invention is that the control unit can selectively open or close the second air flow channel through the air flow channel control mechanism according to the ambient temperature of the fuel cell, thereby solving the problem of poor heat dissipation of the fuel cell in the fuselage and improving the working stability and environmental adaptability of the fuel cell.

[0025] The fuel cell drone provided by the present invention includes a thermal management control device for the fuel cell drone. The second air flow channel arranged on the fuselage can be selectively opened or closed according to the ambient temperature of the fuel cell, thereby realizing automatic control and adjustment of the ambient temperature of the fuel cell, solving the problems of insufficient air intake and poor heat dissipation effect of the fuel cell, improving the working stability and environmental adaptability of the fuel cell, helping to improve the working efficiency of the drone fuel cell, and realizing thermal management control of the fuel cell. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a schematic structural diagram of a fuel cell drone provided by an embodiment of the present invention;

[0027] Figure 2It is a schematic diagram of a state in which a diverter plate in a thermal management control device for a fuel cell drone provided by an embodiment of the present invention is rotated and opened;

[0028] Figure 3 It is a flow chart of the thermal management control method of the fuel cell drone provided by an embodiment of the present invention.

[0029] In the figure:

[0030] 100. Fuel cell; 200. Hydrogen storage bottle;

[0031] 1. fuselage; 11. cabin; 12. first air hole; 13. second air hole; 14. bottom plate;

[0032] 2. Diverter plate; 21. Hinge;

[0033] 3. Driving mechanism; 4. Cooling fan. DETAILED DESCRIPTION

[0034] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0035] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0037] In the description of this embodiment, the terms "upper", "lower", "left", "right", etc., and the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of description and simplified operation, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0038] The embodiment of the present invention first provides a thermal management control device for a fuel cell drone, such as Figure 1 and Figure 2 As shown, the thermal management control device of the fuel cell drone provided by the embodiment of the present invention includes a temperature sensor, an air flow channel control mechanism and a control unit. The temperature sensor is arranged in the fuselage 1 to collect the ambient temperature of the fuel cell 100; a second air hole 13 is arranged on the fuselage 1 to form a second air flow channel, and the air flow channel control mechanism can selectively open or close the second air flow channel to increase or reduce the heat dissipation of the fuel cell 100; the control unit is communicatively connected to the temperature sensor and the air flow channel control mechanism, and the control unit controls the air flow channel control mechanism to open or close the second air flow channel according to the ambient temperature.

[0039] Combination Figure 1 and Figure 2In the embodiment of the present invention, the fuel cell drone comprises a fuselage 1, the fuselage 1 is provided with a cabin 11, the fuel cell 100 is arranged at the top of the fuselage 1 (cabin 11) and forms a heat dissipation space between the bottom plate 14, the bottom plate 14 is provided with a first air hole 12 and a second air hole 13, the first air hole 12 is in a normally open state, the first air hole 12 is realized by hollowing out the bottom plate 14 of the shell structure of the fuselage 1, the first air hole 12 is used to provide air (oxygen) to the fuel cell 100 for electrochemical reaction, and at the same time, the outside air contacts the fuel cell 100 to realize heat exchange; taking the hydrogen fuel cell 100 as an example, the fuel cell 100 is provided with hydrogen by the hydrogen storage bottle 200, and the first air flow channel formed by the first air hole 12 provides oxygen, and the air and the fuel (hydrogen) react electrochemically in the fuel cell 100 to generate electricity and supply the power system of the drone. Among them, the hydrogen storage bottle 200 is arranged between the two fuel cells 100 to reasonably arrange the internal space of the fuselage 1. The fuel cell 100 obtains oxygen and dissipates heat through the first air hole 12 on the fuselage 1. The outside air enters the fuselage 1 (i.e., the cabin 11) through the first air hole 12, which can ensure that the fuel cell 100 in the fuselage 1 has sufficient air intake, and the heat exchange between the surface of the fuel cell 100 and the outside air can be increased to achieve heat dissipation. An air flow channel control mechanism is provided at the second air hole 13, and the control unit and the temperature sensor are provided inside the fuselage 1. By providing the second air hole 13 on the fuselage 1 and providing the temperature sensor in the fuselage 1 to collect the ambient temperature and send it to the control unit, the control unit can control the air flow channel control mechanism to selectively open and close the second air flow channel according to the ambient temperature to increase or reduce the heat dissipation of the fuel cell 100, realize automatic control of the ambient temperature of the fuel cell 100, solve the problem of poor heat dissipation effect of the fuel cell 100 in the fuselage 1, and improve the working stability and environmental adaptability of the fuel cell 100.

[0040] In some embodiments, the air flow channel control mechanism includes a diverter plate 2 and a driving mechanism 3 provided at the second air hole 13, the driving mechanism 3 is communicatively connected to the control unit, the output end of the driving mechanism 3 is connected to the diverter plate 2, and the driving mechanism 3 is used to drive the diverter plate 2 to open or close the second air flow channel.

[0041] Figure 1The left side of the middle bottom plate 14 is shown as the second air hole 13 (without the diverter plate 2), and the right side of the bottom plate 14 is the diverter plate 2 set on the second air hole 13. The diverter plate 2 is set to rotate to open and close the second air hole 13, which is conducive to the control unit to control the opening and closing of the second air flow channel, and realize the automatic control and management of the ambient temperature of the fuel cell 100. In this embodiment, the diverter plate 2 is rotatably connected to the bottom plate 14 through the hinge 21, which has a simple structure, is easy to connect, and has a small weight. By setting a driving mechanism 3 to drive the diverter plate 2 to rotate, the control unit can realize the automatic drive control of the diverter plate 2. The control unit controls the driving mechanism 3 according to the ambient temperature of the fuel cell 100, thereby realizing the selective opening or closing of the second air flow channel for adjustment according to the ambient temperature. When the second air flow channel is opened, the contact area between the outside air and the fuel cell 100 increases, the heat exchange effect is enhanced, and it is conducive to the rapid cooling of the fuel cell 100. When the ambient temperature of the fuel cell 100 is low, the fuel cell 100 only takes in air and dissipates heat through the first air holes 12, which is beneficial for the circulation of heat of the fuel cell 100 in the heat dissipation space to maintain or quickly increase the low ambient temperature of the fuel cell 100.

[0042] In some embodiments, the driving mechanism 3 is fixedly disposed on the fuselage 1. The driving mechanism 3 drives the diverter plate 2 to rotate toward the inside of the fuselage 1 to open the second air flow channel. The driving mechanism 3 drives the diverter plate 2 to rotate from the inside of the fuselage 1 toward the second air hole 13 to close the second air flow channel.

[0043] like Figure 1 As shown, the driving mechanism 3 can adopt a linear driving structure such as a cylinder, or a rotating driving mechanism 3 such as a rotating motor. Taking the linear driving mechanism 3 as an example, the output end of the driving mechanism 3 is hinged with the diverter plate 2, and the driving mechanism 3 is connected to the control unit for communication. The control unit controls the driving mechanism 3 to drive the diverter plate 2 to rotate to open or close the second air flow channel, thereby realizing automatic control of the diverter plate 2, and it is easy to control the rotation angle of the diverter plate 2, and accurately control the air flow and airflow direction. It should be noted that the movement of the diverter plate 2 is a rotation into the fuselage 1, so when the diverter plate 2 rotates to open the second air flow channel, it does not affect the appearance of the fuselage 1.

[0044] In some embodiments, a plurality of first air holes 12 are disposed on the bottom plate 14 of the fuselage 1 of the fuel cell drone, and the plurality of first air holes 12 are spaced and dispersedly disposed on the bottom plate 14 of the fuselage 1 .

[0045] like Figure 1 A plurality of first air holes 12 are provided on the fuselage 1 to form a first air flow channel. The first air holes 12 are arranged on the bottom plate 14 of the fuselage 11 and are arranged directly below the hydrogen storage bottle 200. The first air holes 12 are used to provide air for the fuel cell 100 and to dissipate heat.

[0046] like Figure 1 and Figure 2 As shown, in this embodiment, the fuel cell 100 and the hydrogen storage bottle 200 are arranged inside the cabin 11 and fixed near the top of the cabin 11. A heat dissipation space is formed between the fuel cell 100 and the bottom plate 14 of the fuselage 1. A plurality of first air holes 12 of smaller size are arranged on the bottom plate 14 at a position directly opposite to the middle hydrogen storage bottle 200. The plurality of first air holes 12 on the bottom plate 14 are arranged at intervals, wherein the shape of the first air holes 12 is not limited, and can be rectangular holes or circular holes. External cold air can enter the cabin 11 through the plurality of first air holes 12 on the bottom plate 14, and the hot air in the cabin 11 can be discharged through the first air holes 12, so as to realize heat exchange and sufficient air flow. External air enters through the first air holes 12 to provide sufficient oxygen to the fuel cell 100. The plurality of first air holes 12 are arranged on the bottom plate 14, which is conducive to the dispersed entry of external air, and is conducive to turbulence and uniformization of the temperature and oxygen content in the cabin 11.

[0047] In some embodiments, two second air holes 13 are provided, and the two second air holes 13 are respectively disposed opposite to the two fuel cells 100 .

[0048] like Figure 1 As shown, two second air holes 13 are provided on the fuselage 1, which correspond to the two fuel cells 100 respectively, so as to flexibly control the corresponding second air holes 13 to be opened or closed according to the ambient temperature of the fuel cell 100. It can be understood that the provision of the second air holes 13 is conducive to the outside air entering the cabin 11 and directly impacting the fuel cell 100 so that the cold air can hit the outside of the fuel cell 100 and carry the heat of the fuel cell 100 to discharge and realize heat exchange, heat dissipation and cooling.

[0049] In some embodiments, two second air holes 13 are disposed on both sides of the plurality of first air holes 12 , and the splitter plate 2 is rotatably disposed on one side of the second air holes 13 close to the first air holes 12 .

[0050] like Figure 1 As shown, two driving mechanisms 3 are respectively arranged on both sides of the bottom plate 14, and the output end of the driving mechanism 3 extends toward the diverter plate 2 and is hinged to the diverter plate 2, wherein the driving mechanism 3 is spaced apart from the hinge 21 of the diverter plate 2 for easy rotation control. The second air holes 13 are respectively arranged at a certain angle to the bottom plate 14 on both sides of the bottom plate 14, so that when the two driving mechanisms 3 simultaneously control the two diverter plates 2 to flip inward, there will be no position interference.

[0051] In some embodiments, the thermal management control device of the fuel cell drone also includes a cooling fan 4, which is arranged inside the fuselage 1, with the air inlet of the cooling fan 4 facing the fuel cell 100 and the air outlet of the cooling fan 4 facing the outside of the fuselage 1.

[0052] Preferably, a cooling fan 4 is provided under each fuel cell 100. The cooling fan 4 can increase the air disturbance in the cabin 11, thereby increasing the air flow and heat dissipation, and can quickly discharge the heat on the surface of the fuel cell 100. When the diverter plate 2 is rotated toward the inside of the cabin 11 to open the second air hole 13, the cooling fan 4 can discharge the hot air on the surface of the fuel cell 100 to the second air hole 13, thereby facilitating the rapid discharge of the hot air in the cabin 11 and reducing heat accumulation. At the same time, Figure 2 After the splitter plate 2 rotates to open the second air hole 13, the space between the two splitter plates 2 where the first air hole 12 is located still continues to provide air; the part of the two splitter plates 2 that is away from the first air hole 12 is connected to the outside air through the second air hole 13 to form a second air flow channel, and the gas flow exchange in the second air flow channel achieves heat dissipation. By providing a heat dissipation fan 4, the heat of the fuel cell 100 can be discharged into the outside air faster, achieving rapid heat dissipation and cooling of the fuel cell 100.

[0053] The present invention also provides a thermal management control method for a fuel cell drone, which uses the thermal management control device for a fuel cell drone provided by any of the above embodiments. The thermal management control method for a fuel cell drone comprises the following steps:

[0054] Collecting the ambient temperature T of the fuel cell 100 and sending it to the control unit;

[0055] The control unit selectively opens or closes the second air flow channel through the air flow channel control mechanism according to the ambient temperature T. The above can ensure that the fuel cell 100 operates at a suitable ambient temperature and reduce the impact of ambient temperature changes on the operating performance of the fuel cell 100.

[0056] In the thermal management control method for a fuel cell drone provided by the present invention, the fuel cell 100 arranged in the fuselage 1 is connected to the outside air through a first air flow channel to continuously obtain oxygen and dissipate heat, thereby ensuring that the fuel cell 100 in the fuselage 1 has sufficient air intake; the control unit can selectively open or close the second air flow channel through an air flow channel control mechanism according to the ambient temperature of the fuel cell 100, thereby solving the problems of insufficient air intake and poor heat dissipation of the fuel cell 100 in the fuselage 1, and improving the working stability and environmental adaptability of the fuel cell 100.

[0057] In some embodiments, when the ambient temperature is greater than the first set temperature T1, the control unit controls the second air flow channel to be in an open state through the air flow channel control mechanism to increase the heat exchange between the fuel cell 100 and the outside air; when the ambient temperature T is less than the second set temperature T2, the control unit controls the second air flow channel to be in a closed state through the air flow channel control mechanism to reduce the heat exchange between the fuel cell 100 and the outside air; the first set temperature T1 is greater than the second set temperature T2.

[0058] like Figure 3 As shown in the flow chart, when the ambient temperature T is greater than the first set temperature T1, the control unit detects the state of the second air flow channel, and if the second air flow channel is in a closed state, the second air flow channel is opened through the air flow channel control mechanism, otherwise the second air flow channel is kept in an open state;

[0059] When the ambient temperature T is lower than the second set temperature T2, the control unit detects the state of the second air flow channel. If the second air flow channel is in a closed state, the closed state of the second air flow channel is maintained. Otherwise, the second air flow channel is closed by the air flow channel control mechanism. The above can ensure that the fuel cell 100 always operates at an appropriate temperature between the second set temperature T2 and the first set temperature T1.

[0060] The present invention also provides a fuel cell drone, including the thermal management control device of the fuel cell drone provided by the above embodiment. Through the first air flow channel and the second air flow channel arranged on the fuselage 1, the second air flow channel can be selectively opened or closed according to the ambient temperature of the fuel cell 100, thereby realizing automatic control and adjustment of the ambient temperature of the fuel cell 100, solving the problems of insufficient air intake and poor heat dissipation effect of the fuel cell 100, improving the working stability and environmental adaptability of the fuel cell 100, helping to improve the working efficiency of the drone fuel cell 100, and realizing thermal management control of the fuel cell 100.

[0061] The fuel cell drone provided by the embodiment of the present invention performs a thermal management control method for a fuel cell drone through a thermal management control device for the fuel cell drone to perform thermal management control on the fuel cell 100. Figure 1-Figure 3 , the specific steps are as follows:

[0062] When the drone is powered on (powered on), the fuel cell 100 starts to work, and the cooling fan 4 starts to run accordingly. The heat released by the fuel cell 100 is dissipated to the outside air through the cooling fan 4 and the first air flow channel on the bottom plate 14. At the same time, the outside cold air flows to the fuel cell 100 through the first air hole 12 on the bottom plate 14 to provide oxygen;

[0063] The temperature sensor in the cabin 11 senses the ambient temperature in the cabin 11 and sends it to the control unit. When the internal ambient temperature T is sensed to be greater than the first set temperature T1 (such as 15°C), the control unit first determines the state of the second air flow channel. If the second air flow channel is in a closed state, the first control instruction is sent to the drive mechanism 3. The drive mechanism 3 controls the diverter plate 2 to flip inward, so that the second air flow channel opens, accelerating the heat dissipation of the fuel cell 100, thereby achieving a cooling effect; otherwise, the diverter plate 2 maintains the current state. When the temperature sensor senses that the internal ambient temperature T is lower than the second set temperature T2 (such as 10°C), the control unit again determines the state of the second air flow channel. If the second air flow channel is in a closed state, the diverter plate 2 maintains the current state. Otherwise, the control unit sends a second control instruction to the drive mechanism 3, and the drive mechanism 3 controls the diverter plate 2 to flip outward to close, thereby closing the second air flow channel and reducing the heat dissipation caused by air diversion. A self-circulating heat-insulating environment is formed in the heat dissipation space, so that the ambient temperature of the fuel cell 100 is raised to an appropriate temperature range. The combination of the first air flow channel and the second air flow channel forms a thermal management system that continuously cools the fuel cell 100 and maintains the temperature.

[0064] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, various obvious changes, readjustments and substitutions can be made without departing from the protection scope of the present invention. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A thermal management control device for a fuel cell drone, characterized in that: include: A temperature sensor is arranged in the fuselage (1) of the fuel cell drone to collect the ambient temperature of the fuel cell (100); an air flow channel control mechanism, wherein the body (1) is provided with a second air hole (13) to form a second air flow channel, and the air flow channel control mechanism can selectively open or close the second air flow channel to increase or reduce heat dissipation of the fuel cell (100); A control unit is communicatively connected to the temperature sensor and the air flow channel control mechanism, and the control unit controls the air flow channel control mechanism to open or close the second air flow channel according to the ambient temperature.

2. The thermal management control device for a fuel cell drone according to claim 1, characterized in that: The air flow channel control mechanism comprises a diverter plate (2) arranged at the second air hole (13) and a driving mechanism (3), wherein the driving mechanism (3) is communicatively connected to the control unit, an output end of the driving mechanism (3) is connected to the diverter plate (2), and the driving mechanism (3) is used to drive the diverter plate (2) to open or close the second air flow channel.

3. The thermal management control device for a fuel cell drone according to claim 2, characterized in that: The driving mechanism (3) is fixedly arranged on the fuselage (1); the driving mechanism (3) drives the diverter plate (2) to rotate toward the inside of the fuselage (1) to open the second air flow channel; and the driving mechanism (3) drives the diverter plate (2) to rotate from the inside of the fuselage (1) toward the second air hole (13) to close the second air flow channel.

4. The thermal management control device for a fuel cell drone according to claim 3, characterized in that: Two second air holes (13) are provided, and the two second air holes (13) are respectively arranged facing two fuel cells (100).

5. The thermal management control device for a fuel cell drone according to claim 4, characterized in that: A plurality of first air holes (12) are arranged at intervals and dispersedly on the bottom plate (14) of the fuselage (1) of the fuel cell drone to form a first air flow channel, and the fuel cell (100) arranged in the fuselage (1) is connected to the outside air through the first air flow channel to obtain oxygen and dissipate heat.

6. The thermal management control device for a fuel cell drone according to claim 5, characterized in that: The second air holes (13) are arranged on both sides of the plurality of first air holes (12), and the splitter plate (2) is rotatably arranged on a side of the second air holes (13) close to the first air holes (12).

7. The thermal management control device for a fuel cell drone according to claim 1, characterized in that: It also includes a cooling fan (4), which is arranged inside the fuselage (1), with an air inlet of the cooling fan (4) facing the fuel cell (100) and an air outlet of the cooling fan (4) facing the outside of the fuselage (1).

8. A thermal management control method for a fuel cell drone, characterized in that: Using the thermal management control device of a fuel cell drone according to any one of claims 1 to 7, a thermal management control method of a fuel cell drone comprises the following steps: Collecting the ambient temperature T of the fuel cell (100) and sending it to the control unit; According to the ambient temperature T, the control unit selectively opens or closes the second air flow channel through an air flow channel control mechanism.

9. The thermal management control method for a fuel cell drone according to claim 8, characterized in that: When the ambient temperature is greater than a first set temperature T1, the control unit controls the second air flow channel to be in an open state through the air flow channel control mechanism, so as to increase heat exchange between the fuel cell (100) and the outside air; When the ambient temperature T is lower than a second set temperature T2, the control unit controls the second air flow channel to be in a closed state through the air flow channel control mechanism to reduce heat exchange between the fuel cell (100) and the outside air; the first set temperature T1 is higher than the second set temperature T2.

10. The thermal management control method for a fuel cell drone according to claim 9, characterized in that: When the ambient temperature T is greater than the first set temperature T1, the control unit detects the state of the second air flow channel, and if the second air flow channel is in a closed state, opens the second air flow channel through the air flow channel control mechanism, otherwise, keeps the second air flow channel in an open state; When the ambient temperature T is lower than the second set temperature T2, the control unit detects the state of the second air flow channel. If the second air flow channel is in a closed state, the closed state of the second air flow channel is maintained; otherwise, the second air flow channel is closed by the air flow channel control mechanism.

11. A fuel cell drone, characterized in that: A thermal management control device for a fuel cell drone comprising any one of claims 1 to 7.

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